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Search indexed NASA NTRS and DOE OSTI research on propulsion, heat transfer, battery materials and energy systems. Follow report and document links to the original sources.

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At least 73 records · Page 4
All sourcesNASA NTRSDOE OSTI
NASA NTRS2007

Optical Phased Array Antennas using Coupled Vertical Cavity Surface Emitting Lasers

High data rate communication links are needed to meet the needs of NASA as well as other organizations to develop space-based optical communication systems. These systems must be robust to high radiation environments, reliable, and operate over a wide temperature range. Highly desirable features include beam steering capability, reconfigurability, low power consumption, and small aperture size. Optical communication links, using coupled vertical cavity surface emitting laser radiating elements are promising candidates for the transmit portion of these communication links. In this talk we describe a mission scenario, and how the antenna requirements are derived from the mission needs. We describe a potential architecture for this type of antenna, and outline the advantages and drawbacks of this approach relative to competing technologies. The technology we are proposing used coupled arrays of 1550 nm vertical cavity surface emitting lasers for transmission. The feasibility of coupling these arrays together, to form coherent high-power beams that can be modulated at data rates exceeding 1 Gbps, will be explored. We will propose an architecture that enables electronic beam steering, thus mitigating the need for ancillary acquisition, tracking and beam pointing equipment such as needed for current optical communicatin systems. The beam-steering capability we are proposing also opens the possibility of using this technology for inter-satellite communicatin links, and satellite-to-surface links.

Mueller, Carl H.↗
NASA NTRS2006

Radiator Development for Oxygen Storage on the Moon

Vision for Exploration includes "use of lunar resources to support sustained human space exploration". In a favorable orbit, dark sky could be a valuable resource. Spitzer Space Telescope dewar shell maintained at 35 K. Lunar orbit is favorable. Design of radiator to specific lunar environment. A large patch of lunar sky is permanently dark. Radiator provides reliable and un-interrupted cooling. Applications include: a) Zero-boil-off cryogen storage; b) Separation of lunar volatiles for resource utilization; c) Purify oxygen for astronauts; and d) Scrub air for habitation.

moon↗
NASA NTRS2002

Efficiency of a radiophotoluminescence glass dosemeter for low-earth-orbit space radiation

Chips of a radiophotoluminescence glass dosemeter (RPLG) were used for measurements of space radiation during a 9.8 d Shuttle-Mir mission (STS-91) at an altitude of 400 km and an inclination of 51.65 degrees. Two of RPLG chips were put into each of 59 positions in or on a life-size human phantom. The RPLG values equivalent to 137Cs gamma ray absorbed doses were found to be systematically lower than those of a Mg2SiO4:Tb thermoluminescence dosemeter (TDMS). In comparison with the organ or tissue absorbed dose and dose equivalent values that were estimated using a combination of TDMS and plastic nuclear track detectors, the efficiencies of the RPLG chips were about 80% for the water absorbed dose and about 40% for the dose equivalent. Whereas the percentage values will change during different missions, such additional information obtained from small RPLG chips is useful for improving the reliability of radiation dosimetry in space.

NASA Discipline Radiation Health↗
NASA NTRS1964

Status of solar simulation at Lewis

Evaluation of solar simulators using enclosed sources, in-house measurement facility for testing proposed devices to produce solar simulation, and related research programs

SOLAR SIMULATOR↗
NASA NTRS1973

The applicability of frame imaging from a spinning spacecraft. Volume 1: Summary report

A detailed study was made of frame-type imaging systems for use on board a spin stabilized spacecraft for outer planets applications. All types of frame imagers capable of performing this mission were considered, regardless of the current state of the art. Detailed sensor models of these systems were developed at the component level and used in the subsequent analyses. An overall assessment was then made of the various systems based upon results of a worst-case performance analysis, foreseeable technology problems, and the relative reliability and radiation tolerance of the systems. Special attention was directed at restraints imposed by image motion and the limited data transmission and storage capability of the spacecraft. Based upon this overall assessment, the most promising systems were selected and then examined in detail for a specified Jupiter orbiter mission. The relative merits of each selected system were then analyzed, and the system design characteristics were demonstrated using preliminary configurations, block diagrams, and tables of estimated weights, volumes and power consumption.

Botticelli, R. A.↗
NASA NTRS1977

Hybrid receiver study

The results are presented of a 4 month study to design a hybrid analog/digital receiver for outer planet mission probe communication links. The scope of this study includes functional design of the receiver; comparisons between analog and digital processing; hardware tradeoffs for key components including frequency generators, A/D converters, and digital processors; development and simulation of the processing algorithms for acquisition, tracking, and demodulation; and detailed design of the receiver in order to determine its size, weight, power, reliability, and radiation hardness. In addition, an evaluation was made of the receiver's capabilities to perform accurate measurement of signal strength and frequency for radio science missions.

Stone, M. S.↗
NASA NTRS1979

A high performance microcomputer for space applications

This paper presents a description of a high-performance single board LSI microprocessor (the ATAC-16MS), which forms the core of the attitude and articulation control system of the Galileo spacecraft. The requirements of high speed, low power (20 watts), high reliability and radiation immunity are discussed in terms of the resulting implementation and trade-offs. The problems involved in the transition of a currently operational, fully-militarized processor into a space-qualified processor are summarized. System considerations for the effective use of the ATAC-16MS are also discussed, including the dual block-redundant architecture, the selective application of power for fault isolation and the trade-offs between low power dissipation and high performance of the peripheral circuitry for space applications.

Jack, L.↗
NASA NTRS1988

An approach to the design of a simple, radiation hard, highly integrated and reliable, lightweight satellite bus

A spacecraft system concept has been developed which uses ion propulsion and a small, simple, lightweight design approach to carry out a focused lunar science mission. The design relies on existing technology to achieve high reliability and the possibility of a near-term launch. Key characteristics of the mission are highly focused objectives, low launch costs, minimization of development risks and design simplicity. The spacecraft for the lunar mission is described with particular emphasis on the design and reliability approaches used. The degree of adaptability of this basic class of spacecraft bus is discussed with particular emphasis on its application as a technology testbed vehicle. Several potential mission applications are reviewed.

Nock, K. T.↗
NASA NTRS1992

Field programmable gate arrays: Evaluation report for space-flight application

Field Programmable Gate Arrays commonly called FPGA's are the newer generation of field programmable devices and offer more flexibility in the logic modules they incorporate and in how they are interconnected. The flexibility, the number of logic building blocks available, and the high gate densities achievable are why users find FPGA's attractive. These attributes are important in reducing product development costs and shortening the development cycle. The aerospace community is interested in incorporating this new generation of field programmable technology in space applications. To this end, a consortium was formed to evaluate the quality, reliability, and radiation performance of FPGA's. This report presents the test results on FPGA parts provided by ACTEL Corporation.

Sandoe, Mike↗
NASA NTRS2001

Overview of Non-Volatile Testing and Screening Methods

Testing methods for memories and non-volatile memories have become increasingly sophisticated as they become denser and more complex. High frequency and faster rewrite times as well as smaller feature sizes have led to many testing challenges. This paper outlines several testing issues posed by novel memories and approaches to testing for radiation and reliability effects. We discuss methods for measurements of Total Ionizing Dose (TID).

Irom, Farokh↗
NASA NTRS1994

Inverter Matrix for the Clementine Mission

An inverter matrix test circuit was designed for the Clementine space mission and is built into the RRELAX (Radiation and Reliability Assurance Experiment). The objective is to develop a circuit that will allow the evaluation of the CMOS FETs using a lean data set in the noisy spacecraft environment.

CMOS FETs spacecraft environment RRELAX orbit moon↗
NASA NTRS2008

Considerations for IC and Component Selection for Space Systems

This viewgraph presentation addresses the integrated cycling and component selection technologies for aerospace systems. The topics include: 1) Semiconductors: The Evolution of ICs - Availability and Technology; 2) IC Selection Requirements - three fields of thought, "The Good", "The Bad" and "The Ugly"; 3) Reliability and Radiation; 4) Radiation Perspective-Four methods of selecting ICs for space systems, Guaranteed hardness, historical ground-based radiation data, historical flight usage, and unknown assurance; 5) Understanding Risk, including risk trade space and ASICs and FPGA sample selection criteria.

LaBel, Kenneth A.↗
NASA NTRS2015

Compendium of Current Single Event Effects for Candidate Spacecraft Electronics for NASA

NASA spacecraft are subjected to a harsh space environment that includes exposure to various types of ionizing radiation. The performance of electronic devices in a space radiation environment are often limited by their susceptibility to single event effects (SEE). Ground-based testing is used to evaluate candidate spacecraft electronics to determine risk to spaceflight applications. Interpreting the results of radiation testing of complex devices is and adequate understanding of the test condition is critical. Studies discussed herein were undertaken to establish the application-specific sensitivities of candidate spacecraft and emerging electronic devices to single-event upset (SEU), single-event latchup (SEL), single-event gate rupture (SEGR), single-event burnout (SEB), and single-event transient (SET). For total ionizing dose (TID) and displacement damage dose (DDD) results, see a companion paper submitted to the 2015 Institute of Electrical and Electronics Engineers (IEEE) Nuclear and Space Radiation Effects Conference (NSREC) Radiation Effects Data Workshop (REDW) entitled "compendium of Current Total Ionizing Dose and Displacement Damage for Candidate Spacecraft Electronics for NASA by M. Campola, et al.

spacecraft electronics↗